冲压发动机用轴对称进气道设计和试验  

Design and wind tunnel test of an axisymmetric inlet for ramjet engine

作　　者：王健[1,2] 李宏东[2] 朱守梅[2] 朱璞[2] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]北京动力机械研究所,北京100074

出　　处：《推进技术》2009年第6期682-686,共5页Journal of Propulsion Technology

摘　　要：完成了一种Ma=2.5～4.0冲压发动机用超声速轴对称混合式进气道模型的设计,通过数值模拟和风洞试验,获得了马赫数Ma=2.5,3.0,3.5,4.0,攻角α=0°,3°,6°,8°条件下的超声速轴对称混合式进气道性能。试验结果表明,随着马赫数的增加,总压恢复系数大幅度下降,亚临界稳定范围变窄,流量系数逐渐增加;随着攻角的增大,总压恢复系数和流量系数总体都呈降低趋势,在Ma≥3.0,α=6°时,进气道性能的下降小于5%,亚临界稳定范围变窄。The design of an axisymmetic and mixed-compressed inlet model for the ramjet operating Mach number Ma=2.5~4.0 was conducted. By using numerical simulations and wind tunnel tests, the inlet performance for the operating Mach number Ma=2.5, 3.0, and 4.0 with the angle of the attack (AOA) α= 0°, 3°, 6° and 8° was obtained. The tests show that with an increase of the flight Mach number, the total pressure recovery coefficient is reduced dramatically, the sub-critical stable operating range is shortened and the ...

关 键 词：冲压喷气发动机 进气道 进气道性能+ 模型设计 风洞试验 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]